EPPLER 1230 AIRFOIL (e1230-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 1230 AIRFOIL (e1230-il) Reynolds number: 500,000 Max Cl/Cd: 85.57 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e1230-il-500000.txt Download as CSV file: xf-e1230-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 1230 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.750 -0.6182 0.08681 0.08379 -0.0583 1.0000 0.0154
-14.500 -0.6554 0.07607 0.07288 -0.0650 1.0000 0.0152
-14.250 -0.6861 0.06750 0.06414 -0.0703 1.0000 0.0151
-14.000 -0.7121 0.06072 0.05719 -0.0740 1.0000 0.0150
-13.750 -0.7346 0.05525 0.05155 -0.0764 1.0000 0.0150
-13.500 -0.7542 0.05074 0.04688 -0.0775 1.0000 0.0149
-13.250 -0.7716 0.04695 0.04293 -0.0777 1.0000 0.0150
-13.000 -0.7870 0.04371 0.03953 -0.0771 1.0000 0.0150
-12.750 -0.8006 0.04094 0.03660 -0.0759 1.0000 0.0150
-12.500 -0.8138 0.03858 0.03410 -0.0739 1.0000 0.0151
-12.250 -0.8271 0.03669 0.03206 -0.0709 1.0000 0.0151
-12.000 -0.8419 0.03525 0.03050 -0.0666 1.0000 0.0152
-11.750 -0.8592 0.03421 0.02935 -0.0608 1.0000 0.0152
-11.500 -0.8677 0.03303 0.02804 -0.0561 1.0000 0.0153
-11.250 -0.8714 0.03189 0.02676 -0.0521 1.0000 0.0154
-11.000 -0.8423 0.03021 0.02484 -0.0543 0.9967 0.0155
-10.750 -0.8155 0.02753 0.02200 -0.0563 0.9941 0.0158
-10.500 -0.7857 0.02591 0.02030 -0.0580 0.9902 0.0161
-10.250 -0.7517 0.02464 0.01898 -0.0603 0.9874 0.0164
-10.000 -0.7198 0.02352 0.01779 -0.0620 0.9833 0.0168
-9.750 -0.6856 0.02243 0.01663 -0.0640 0.9796 0.0172
-9.500 -0.6533 0.02141 0.01552 -0.0654 0.9748 0.0177
-9.250 -0.6201 0.02044 0.01447 -0.0670 0.9698 0.0182
-9.000 -0.5917 0.01963 0.01357 -0.0674 0.9615 0.0186
-8.750 -0.5686 0.01838 0.01231 -0.0671 0.9508 0.0192
-8.500 -0.5434 0.01755 0.01148 -0.0668 0.9383 0.0198
-8.250 -0.5133 0.01678 0.01068 -0.0674 0.9269 0.0207
-8.000 -0.4714 0.01598 0.00980 -0.0704 0.9177 0.0218
-7.750 -0.4262 0.01494 0.00874 -0.0744 0.9033 0.0232
-7.500 -0.3806 0.01430 0.00799 -0.0782 0.8795 0.0253
-7.250 -0.3488 0.01375 0.00731 -0.0792 0.8474 0.0276
-7.000 -0.3236 0.01349 0.00687 -0.0786 0.8164 0.0300
-6.750 -0.3020 0.01312 0.00640 -0.0774 0.7899 0.0332
-6.500 -0.2801 0.01280 0.00600 -0.0762 0.7662 0.0379
-6.250 -0.2579 0.01250 0.00563 -0.0751 0.7451 0.0458
-6.000 -0.2357 0.01223 0.00534 -0.0740 0.7255 0.0572
-5.750 -0.2124 0.01205 0.00511 -0.0730 0.7071 0.0684
-5.500 -0.1889 0.01188 0.00490 -0.0721 0.6900 0.0787
-5.250 -0.1651 0.01175 0.00471 -0.0713 0.6739 0.0885
-5.000 -0.1411 0.01158 0.00452 -0.0705 0.6583 0.0991
-4.750 -0.1172 0.01140 0.00433 -0.0697 0.6437 0.1109
-4.500 -0.0933 0.01123 0.00414 -0.0689 0.6300 0.1246
-4.000 -0.0459 0.01082 0.00378 -0.0672 0.6039 0.1682
-3.750 -0.0234 0.01051 0.00360 -0.0663 0.5919 0.2125
-3.500 -0.0024 0.01009 0.00339 -0.0651 0.5801 0.2817
-3.250 0.0180 0.00957 0.00319 -0.0639 0.5695 0.3748
-3.000 0.0370 0.00910 0.00307 -0.0623 0.5591 0.4835
-2.750 0.0603 0.00894 0.00310 -0.0612 0.5487 0.5534
-2.500 0.0852 0.00901 0.00315 -0.0604 0.5384 0.5879
-2.250 0.1116 0.00908 0.00320 -0.0599 0.5280 0.6093
-2.000 0.1379 0.00923 0.00325 -0.0593 0.5184 0.6249
-1.750 0.1648 0.00936 0.00334 -0.0589 0.5090 0.6363
-1.500 0.1914 0.00952 0.00340 -0.0585 0.5003 0.6458
-1.250 0.2186 0.00965 0.00346 -0.0581 0.4915 0.6552
-1.000 0.2449 0.00979 0.00350 -0.0577 0.4827 0.6623
-0.750 0.2722 0.00988 0.00354 -0.0574 0.4744 0.6701
-0.500 0.2985 0.00996 0.00355 -0.0570 0.4661 0.6765
-0.250 0.3256 0.01004 0.00359 -0.0567 0.4588 0.6841
0.000 0.3520 0.01010 0.00363 -0.0562 0.4513 0.6927
0.250 0.3779 0.01025 0.00372 -0.0557 0.4443 0.7023
0.500 0.4049 0.01026 0.00375 -0.0554 0.4374 0.7096
0.750 0.4313 0.01038 0.00380 -0.0550 0.4303 0.7157
1.000 0.4583 0.01046 0.00383 -0.0548 0.4238 0.7204
1.250 0.4855 0.01048 0.00384 -0.0547 0.4174 0.7244
1.500 0.5121 0.01059 0.00388 -0.0544 0.4112 0.7281
1.750 0.5394 0.01067 0.00393 -0.0543 0.4057 0.7316
2.000 0.5668 0.01075 0.00397 -0.0542 0.4000 0.7349
2.250 0.5933 0.01083 0.00400 -0.0540 0.3942 0.7380
2.500 0.6201 0.01091 0.00407 -0.0538 0.3888 0.7410
2.750 0.6474 0.01096 0.00413 -0.0538 0.3836 0.7445
3.000 0.6741 0.01107 0.00420 -0.0536 0.3785 0.7481
3.250 0.7001 0.01127 0.00431 -0.0533 0.3734 0.7513
3.500 0.7274 0.01130 0.00439 -0.0533 0.3694 0.7545
3.750 0.7542 0.01137 0.00449 -0.0531 0.3647 0.7582
4.000 0.7802 0.01149 0.00459 -0.0529 0.3601 0.7622
4.250 0.8057 0.01171 0.00475 -0.0526 0.3551 0.7661
4.500 0.8327 0.01177 0.00486 -0.0525 0.3517 0.7699
4.750 0.8591 0.01185 0.00499 -0.0523 0.3478 0.7743
5.000 0.8849 0.01199 0.00513 -0.0520 0.3440 0.7796
5.250 0.9101 0.01219 0.00530 -0.0517 0.3399 0.7853
5.500 0.9355 0.01234 0.00550 -0.0513 0.3362 0.7918
5.750 0.9613 0.01242 0.00565 -0.0511 0.3328 0.7997
6.000 0.9864 0.01252 0.00582 -0.0507 0.3293 0.8101
6.250 1.0104 0.01263 0.00601 -0.0501 0.3259 0.8285
6.500 1.0322 0.01272 0.00628 -0.0489 0.3225 0.8896
6.750 1.0784 0.01299 0.00665 -0.0530 0.3188 0.9668
7.000 1.1147 0.01319 0.00690 -0.0551 0.3154 1.0000
7.250 1.1375 0.01337 0.00708 -0.0544 0.3122 1.0000
7.500 1.1599 0.01359 0.00729 -0.0536 0.3091 1.0000
7.750 1.1819 0.01389 0.00755 -0.0527 0.3061 1.0000
8.000 1.2046 0.01423 0.00787 -0.0520 0.3030 1.0000
8.250 1.2271 0.01441 0.00811 -0.0513 0.3008 1.0000
8.500 1.2488 0.01462 0.00835 -0.0503 0.2980 1.0000
8.750 1.2699 0.01484 0.00859 -0.0493 0.2951 1.0000
9.000 1.2905 0.01510 0.00885 -0.0482 0.2923 1.0000
9.250 1.3110 0.01544 0.00918 -0.0472 0.2895 1.0000
9.500 1.3328 0.01586 0.00959 -0.0465 0.2865 1.0000
9.750 1.3531 0.01609 0.00989 -0.0454 0.2844 1.0000
10.000 1.3732 0.01635 0.01021 -0.0443 0.2818 1.0000
10.250 1.3931 0.01664 0.01054 -0.0433 0.2790 1.0000
10.500 1.4125 0.01696 0.01088 -0.0422 0.2763 1.0000
10.750 1.4310 0.01736 0.01127 -0.0410 0.2731 1.0000
11.000 1.4503 0.01783 0.01175 -0.0400 0.2698 1.0000
11.250 1.4683 0.01814 0.01215 -0.0388 0.2673 1.0000
11.500 1.4862 0.01850 0.01258 -0.0376 0.2644 1.0000
11.750 1.5036 0.01890 0.01302 -0.0364 0.2614 1.0000
12.000 1.5200 0.01937 0.01351 -0.0352 0.2584 1.0000
12.250 1.5362 0.02002 0.01412 -0.0340 0.2547 1.0000
12.500 1.5518 0.02047 0.01470 -0.0327 0.2521 1.0000
12.750 1.5674 0.02099 0.01530 -0.0316 0.2490 1.0000
13.000 1.5823 0.02157 0.01595 -0.0304 0.2458 1.0000
13.250 1.5957 0.02228 0.01668 -0.0292 0.2425 1.0000
13.500 1.6079 0.02315 0.01754 -0.0279 0.2388 1.0000
13.750 1.6217 0.02388 0.01840 -0.0269 0.2359 1.0000
14.000 1.6349 0.02470 0.01931 -0.0260 0.2324 1.0000
14.250 1.6461 0.02568 0.02034 -0.0250 0.2287 1.0000
14.500 1.6544 0.02691 0.02157 -0.0239 0.2250 1.0000
14.750 1.6651 0.02805 0.02281 -0.0231 0.2216 1.0000
15.000 1.6759 0.02923 0.02410 -0.0225 0.2176 1.0000
15.250 1.6833 0.03071 0.02563 -0.0217 0.2134 1.0000
15.500 1.6859 0.03260 0.02752 -0.0209 0.2092 1.0000
15.750 1.6948 0.03411 0.02916 -0.0205 0.2051 1.0000
16.000 1.6994 0.03603 0.03116 -0.0201 0.2003 1.0000
16.250 1.6977 0.03854 0.03369 -0.0196 0.1956 1.0000
16.500 1.7010 0.04071 0.03596 -0.0194 0.1910 1.0000
16.750 1.7001 0.04334 0.03867 -0.0192 0.1857 1.0000
17.000 1.6916 0.04677 0.04212 -0.0191 0.1806 1.0000
17.250 1.6909 0.04953 0.04499 -0.0192 0.1754 1.0000
17.500 1.6810 0.05333 0.04883 -0.0193 0.1697 1.0000
17.750 1.6704 0.05729 0.05286 -0.0196 0.1644 1.0000
18.000 1.6587 0.06147 0.05712 -0.0201 0.1584 1.0000
18.250 1.6395 0.06657 0.06225 -0.0208 0.1530 1.0000
18.500 1.6269 0.07105 0.06681 -0.0215 0.1469 1.0000
18.750 1.6036 0.07685 0.07265 -0.0225 0.1413 1.0000
19.000 1.5879 0.08183 0.07770 -0.0235 0.1354 1.0000
19.250 1.5638 0.08798 0.08389 -0.0249 0.1298 1.0000
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